WO2022223905A1 - Ensemble d'anneau de turbine monté sur entretoise - Google Patents
Ensemble d'anneau de turbine monté sur entretoise Download PDFInfo
- Publication number
- WO2022223905A1 WO2022223905A1 PCT/FR2022/050688 FR2022050688W WO2022223905A1 WO 2022223905 A1 WO2022223905 A1 WO 2022223905A1 FR 2022050688 W FR2022050688 W FR 2022050688W WO 2022223905 A1 WO2022223905 A1 WO 2022223905A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- ring
- radial
- assembly
- flange
- upstream
- Prior art date
Links
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 47
- 239000000463 material Substances 0.000 claims abstract description 13
- 239000011153 ceramic matrix composite Substances 0.000 claims abstract description 6
- 125000006850 spacer group Chemical group 0.000 claims description 41
- 239000002184 metal Substances 0.000 claims description 20
- 238000002347 injection Methods 0.000 claims description 17
- 239000007924 injection Substances 0.000 claims description 17
- 238000007789 sealing Methods 0.000 claims description 12
- 230000000295 complement effect Effects 0.000 claims description 6
- 230000004323 axial length Effects 0.000 claims description 3
- 230000000284 resting effect Effects 0.000 claims 2
- 210000003462 vein Anatomy 0.000 description 8
- 238000001816 cooling Methods 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 239000006185 dispersion Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000007769 metal material Substances 0.000 description 3
- 238000009423 ventilation Methods 0.000 description 3
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical group FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
- F05D2300/6033—Ceramic matrix composites [CMC]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the invention relates to a turbine ring assembly for a turbomachine in which the assembly comprises a plurality of angular sectors of a ceramic matrix composite material ring placed end to end to form a turbine ring.
- the field of application of the invention is in particular that of aeronautical gas turbine engines.
- the invention is however applicable to other turbomachines, for example industrial turbines.
- CMC materials have good mechanical properties making them suitable for forming structural elements and advantageously retain these properties at high temperatures.
- the use of CMC materials has advantageously made it possible to reduce the cooling flow to be imposed during operation and therefore to increase the performance of the turbomachines.
- the use of CMC materials advantageously makes it possible to reduce the mass of the turbomachines and to reduce the hot expansion effect encountered with the metal parts.
- documents FR 2540939, GB 2480766, EP 1 350927, US 2014/0271145, US 2012/082540 and FR 2955898 which disclose turbine ring assemblies.
- the ring sectors comprise an annular base whose inner face defines the inner face of the turbine ring and an outer face from which extend radially two legs whose ends are held between the two flanges of a structure metal ring support.
- CMC ring sectors thus makes it possible to significantly reduce the ventilation required to cool the turbine ring.
- the CMC having a different mechanical behavior from a metallic material, its integration as well as the way of positioning it within the turbine had to be redesigned. Indeed, CMC does not support shrunk assemblies (usually used for metal rings) and its thermal expansion is lower than a metal material.
- CMC ring sectors increase the number of parts required for its integration on the turbine casing, which increases the cost and weight of the assembly and requires complex assembly operations (shrinking of bushings, mounting pins, etc.).
- the main object of the present invention is therefore to propose a turbine ring assembly which does not have the aforementioned drawbacks while having a reduced mass and reducing all the more the intensity of the mechanical stresses to which the ring sectors in CMC are subjected during the operation of the turbine.
- a turbine ring assembly extending around an axis, the assembly comprising a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a support structure for ring held by a turbine casing.
- Each ring sector comprises a base from which extend radially outwards an upstream attachment lug and a downstream attachment lug spaced axially from each other.
- the turbine ring assembly according to the invention is remarkable in particular in that it further comprises a spacer mechanically connected to the ring support and comprising a first radial flange bearing against the upstream attachment lugs of the sectors of ring, and, for each ring sector, at least two transverse pins and a radial spring, each transverse pin passing through the upstream attachment lug and the downstream attachment lug of the ring sector and the ring support to maintain the ring sector and the ring support secured to each other, and the radial spring being held in abutment against the ring sector on the one hand and against the ring support on the other part, the ring support further comprising a second radial flange bearing against the downstream attachment lugs of the ring sectors, the upstream attachment lug and the downstream attachment lug of each ring sector being arranged axially between the first radial flange and the second xth radial flange.
- the architecture of the turbine ring assembly according to the invention thus makes it possible to offer radial and axial support for each ring sector in CMC material not using support techniques for metal rings and made in such a way to control its position and prevent it from vibrating, on the one hand, while allowing the ring sector, and by extension the ring, to deform freely under the effects of temperature rises and variations pressure, in particular thanks to a reduced number of metal parts at the interface.
- the radial retention of a ring of CMC material is ensured, on the one hand, by said at least two pins passing through each ring sector and the ring support by means of axial holes provided for this effect, and, on the other hand, by means of the metal spring placed between two pins and being in radial support between the ring sector and the ring support.
- the spring makes it possible in particular to maintain the sectors of rings arranged in the same radial position.
- the axial retention of a ring made of CMC material is ensured, on the one hand, by the attachment of the ring support to the spacer, for example via at least one assembly formed by a screw and a nut, fixing the ring support and the spacer together outside the casing, and, on the other hand, by the plane contact between the tab upstream attachment of the ring and the spacer and by the plane contact between the ring support and the downstream attachment lug of the ring.
- this architectural configuration of the turbine ring assembly offers a solution devoid of a bolted connection between the turbine ring and the ring support structure and the casing, the connection being made by means of the transverse pins, which makes it possible to reduce the total mass of the assembly significantly.
- the elimination of the bolted connections also makes it possible to arrange the parts of the ring assembly differently, which also allows a saving in mass by reducing the number of elements constituting the turbine ring assembly.
- said first radial flange may comprise a first portion and a second portion radially inside the first portion, the second portion comprising a first tab and a second tab axially spaced apart one from the other and both secured to the first portion, the first lug being axially upstream of the second lug, and the second lug bearing against the upstream attachment lug.
- the first radial flange of the spacer thus makes it possible to minimize the tangential stress in the metal parts ensuring the maintenance of the ring, on the one hand, and to compensate for the high manufacturing dispersion of the CMC ring sectors, in particular the length axial of the rings.
- the production of the spacer in one piece makes it possible to significantly reduce the number of parts necessary to maintain the ring.
- the manufacturing tolerances are less strict, the spacer making it possible to compensate for the differences between the ring sectors, which a 360° flange cannot do.
- the downstream leg of said first radial flange may comprise a first end which is integral with the first portion of the first radial flange and a second end which is free and opposite the first end, the downstream tab further comprising radial slots regularly spaced angularly and each extending from the second end to a circular orifice, the number of radial slots being equal at most to the number of sectors d 'ring.
- the circular orifices into which the slots open allow the stress concentration in the area to be reduced.
- the number of slots can be equal to the number of ring sectors. In this way, the contact between the spacer and each ring sector of the assembly is ensured regardless of the manufacturing dispersion of the CMC ring sectors.
- the ring sectors can be paired two by two or three by three in order to create pairs of two or three rings having substantially identical axial lengths. The pairs of ring sectors are then mounted side by side on the motor to form the ring.
- the number of slots required on the downstream leg of the first radial flange of the spacer can be divided by two or three. This reduction in the number of slots makes it possible to increase the robustness of the ventilation of the device all the more by improving the sealing between the sector outside the vein and the vein sector, in particular the sealing of the cavity located at the level of the part radially top of the ring.
- the spacer may comprise a ring disposed around the turbine ring, and the ring support may comprise a shroud disposed radially between the turbine ring and the spacer crown.
- the crown of the spacer can comprise injection orifices and the shroud of the ring support comprises complementary injection orifices radially offset with respect to the orifices of injection. In other words, no additional injection orifice of the ring support is radially aligned with an injection orifice of the spacer.
- the injection ports and the complementary injection ports supply cold air at high pressure, generally air taken from the outlet of the high pressure compressor, making it possible to pressurize the cavities located between the ring and the spacer or in ring and ring holder.
- this injection of air makes it possible to pressurize the sector outside the vein and thus to improve the tightness between the sector outside the vein and the sector the vein.
- the assembly may further comprise a C-ring joint extending between the crown of the spacer and the shroud of the ring support, the C-ring joint being coaxial with the crown of the spacer and the ferrule of the ring support.
- the C-seal placed between the spacer and the ring support makes it possible to minimize any leakage between these two parts and to improve the robustness of the cooling device of the rings.
- the ring support structure may further comprise a first radial support flange and a second radial support flange axially spaced from the first radial support flange, each pin transverse passing through the first radial support flange and the second radial support flange.
- the radial spring may comprise a metal plate having at least one curvature in a first direction parallel to the axial direction.
- the metal plate forming the radial spring can be corrugated or curved, the bump extending radially to exert a force in the radial direction of the turbine ring.
- the radial spring further comprises a tongue projecting from the top of the crown in a second direction orthogonal to the first direction and extending along the crown in a third direction orthogonal to the first and second directions over a length less than the length of the metal plate in the third direction, the tongue being arranged between the first and second radial support flanges to form an axial abutment to the spring.
- the spring tab thus prevents the spring from moving axially.
- the assembly may further comprise an L-shaped sealing tongue disposed at each junction between two adjacent ring sectors, each sealing tongue comprising a large portion s extending axially and a small portion extending radially, the small portion being integral with the large portion at an upstream end of the large portion.
- the tab extending in the circumferential direction between two adjacent ring sectors over the entire axial length of the ring sectors, this forms a seal providing sealing between the vein sector and the non-vein sector.
- the L-shape of the tongue avoids any impact between the tongue and the second radial flange.
- the assembly may further comprise a thermal protection ring mounted radially inside the second radial flange, the second radial flange of the ring support further comprising discharge holes passing axially through said second radial flange of the ring support.
- the relief holes and the thermal protection ring ensure sealing between the non-vein sector and the inlet sector, in particular in the cavities located downstream of the ring sectors.
- the thermal protection ring can be an annular metal sheet segmented at only one place of its circumference to better adapt to the radial dimensions.
- the invention also relates to a turbomachine comprising an assembly as defined previously.
- Figure 1 is a schematic sectional view along a plane including the axial direction and the radial direction of a turbine ring assembly according to the invention.
- Figure 2 shows a schematic sectional and perspective view of the spacer of the turbine assembly of Figure 1.
- Figure 3 shows a schematic perspective view of the radial spring of the turbine assembly of Figure 1.
- Figure 4 shows a sectional view of the ring assembly at the level of a radial spring along a sectional plane comprising the axial direction and the radial direction.
- Figure 5 shows a sectional view of the ring assembly at a ring sector along a section plane including the radial direction and orthogonal to the axial direction.
- Figure 1 schematically represents a turbine ring assembly 2 according to the invention.
- Figure 1 is a sectional view along a plane including the radial direction and the axial direction.
- This assembly 2 comprises in particular a turbine ring 4 made of ceramic matrix composite material (CMC) centered on a longitudinal axis X-X, a metallic ring support structure 6 fixed to a turbine casing of which only one attachment portion 32 is represented in figure 1 for more readability.
- the turbine ring 4 surrounds a set of turbine blades not shown.
- upstream and downstream are used in reference to the direction of flow of the gas flow F through the blades indicated by an arrow.
- the turbine ring 4 is formed of a plurality of angular ring sectors 10 which are placed end to end in the circumferential direction to form a ring.
- the arrow D A indicates the axial direction of the turbine ring while the arrow DR indicates the radial direction of the turbine ring.
- Each angular ring sector 10 has a section substantially in the shape of an inverted Pi (or TT) with a base 12 provided with an internal face 12a which defines an angular portion of the internal face of the turbine ring 4 and which is typically provided with an abradable coating layer 13 also acting as a thermal and environmental barrier.
- Two attachment lugs extend radially from the outer face 12b of the base 12 opposite the inner face 12a. These attachment lugs 14 and 16 extend over the entire width of each ring sector 10 (in the circumferential direction).
- the ring assembly 2 further comprises a spacer 20 attached to the structure ring support 6 using a bolt 300 and a nut 302.
- the spacer 20 comprises a crown 202 extending around the X-X axis and having a downstream end 204 and an upstream end 206.
- the spacer 20 further comprises a first radial attachment flange 208 extending radially towards the outside from the downstream end 204 of the spacer 20
- the ring support structure 6 includes a ferrule 60 extending around the X-X axis and includes a second attachment flange 62 extending radially outward from the ferrule 60.
- the second radial attachment flange 62 of the shroud 60 of the ring support structure 6, the attachment portion 32 of the turbine casing and the first radial attachment flange 208 of the spacer 20 are fixed together to using the bolt 300 which crosses the three elements axially and the nut 302.
- the ring support structure 6 further comprises a first radial attachment flange 64 for the ring 4 and a second radial attachment flange 66 for the ring 4 each extending inwards in the radial direction. DR, i.e. towards turbine ring 4.
- the first radial attachment flange 64 is placed downstream of the second radial attachment flange 66.
- the first radial attachment flange 64 and the second radial attachment flange 66 are arranged axially between the downstream attachment lug 14 and the upstream attachment lug 16 of the ring sectors 10.
- the turbine ring assembly 2 further comprises transverse pins 40, each transverse pin 40 being formed in a single piece and crossing axially, in the direction of the gas flow F, the upstream tab 16 of a ring sector 10, the second radial attachment flange 66 of the ring support structure 6, the first radial attachment flange 64 of the ring support structure 6, and the downstream attachment bracket 14.
- Each transverse pin 40 comprises a downstream end 402, an upstream end 404, the upstream end comprising an axial orifice 406 to facilitate removal of the pin 40.
- the spacer 20 further comprises an upstream radial flange 210 extending radially inward from the upstream end 206 of the spacer 20.
- the upstream radial flange 210 comprises, in the radial direction DR, a first end
- first portion 2103 and a second portion 2104 free and opposite the first end 2101, a first portion 2103 and a second portion 2104, the first portion 2103 extending radially between the first end 2101 and the second portion 2104, and the second portion 2104 extending radially between the first portion 2103 and the second end 2102.
- the second portion 2104 of the upstream radial flange 210 of the spacer 20 comprises an upstream leg 2105 and a downstream leg 2106.
- the upstream leg 2105 and the downstream leg 2106 of the second portion 2104 of the upstream radial flange 210 form two distant rings from each other in the axial direction D A .
- the downstream tab 2106 of the upstream radial flange 210 bears against the upstream attachment tab 16 of the ring sectors 10.
- the upstream attachment lug 16 of the ring sectors 10 is thus axially disposed, in the direction of the flow F, between the downstream lug 2106 of the upstream radial flange 210 of the spacer 20 and the second radial flange of hook 66 of the ring support structure 6.
- upstream leg 2105 of the second portion 2104 of the upstream radial flange 210 comprises a radial groove 2107 on its radially inner end inside which is inserted a seal 2108.
- the spacer 20 can be a part of revolution (that is to say 360°) or else be made by assembling a plurality of spacer sectors placed end to end.
- the ring support structure 6 further comprises a downstream radial flange 68 disposed axially downstream of the first attachment flange 64 and downstream of the downstream attachment lug 14 of the ring sectors 10.
- the downstream lug of attachment 14 of the ring sectors 10 is thus arranged axially, in the direction of flow F, between the first radial attachment flange 64 and the downstream radial flange 68 of the ring support structure 6.
- the downstream radial flange 68 bears against the downstream attachment lug 16 of the ring sectors 10.
- the ring sectors 10 are thus held axially in contact between the downstream leg 2106 of the upstream radial flange 210 of the spacer 20 and the downstream radial flange 68 of the ring support structure 6.
- the crown 202 of the spacer 20 further comprises injection orifices 220 radially passing through the crown 202 and the ferrule 60 of the ring support structure 6 further comprises complementary injection orifices 600 radially passing through the ferrule 60
- the injection ports 200 and the complementary injection ports 600 are not radially aligned. They can be staggered relative to each other.
- the injection ports 200 and the complementary injection ports 600 make it possible to route cooling air taken from the high pressure compressor into the cavities located between the ring support structure 6 and the turbine ring 4 notably.
- the downstream radial flange 68 of the ring support structure 6 further comprises relief holes 680 allowing cooling air to be routed into the cavity located downstream of the downstream radial flange 68.
- the ring assembly 2 further comprises a C-shaped metal ring seal 50 disposed radially between the spacer 20 and the ring support structure 6 to improve sealing.
- the ring assembly 2 also comprises a metal thermal protection ring 52 arranged radially between the downstream radial flange 68 of the ring support structure 6 and the duct 45 inside which the gas flow flows. f.
- the downstream tab 2106 of the upstream radial flange 210 of the spacer 20 further comprises a plurality of radial slots 222 regularly spaced angularly along the circumferential direction.
- the slots radials 222 are open and extend radially from the second end 2102 of the upstream radial flange 210 to a circular orifice 224 to reduce the accumulation of stresses.
- the number of radial slots 222 is equal to the number of ring sectors 10 forming the turbine ring 4, or is equal to the number of ring sectors 10 divided by two or three.
- FIG. 3 is shown schematically in perspective a radial spring 70.
- the radial spring 70 comprises a corrugated metal plate 71, the corrugation being arranged in a first direction tangent to the circumferential direction of the turbine ring 4 when the radial spring 70 is mounted on the turbine ring assembly 2.
- the metal plate 71 thus comprises a central boss 72 from which projects radially a tongue 73 which also extends in a second direction orthogonal to the first direction and parallel to the axial direction D A when the radial spring 70 is mounted on the turbine ring assembly 2.
- the length of the tongue in the axial direction D A is less than the length of the metal plate 71.
- the central boss 72 is surrounded by two tabs 74 having a boss opposite the central boss 72.
- the tongue 73 is axially disposed and held between the first radial flange 64 and the second radial attachment flange 66.
- the radial spring 70 bears, via its lugs 74, against the base 12 of the ring sector 10 in which it is mounted and against the ferrule 60 of the ring support structure 6 via its tab 73.
- the ring assembly further comprises a sealing tongue 8 having an L shape with a small portion 82 and a large portion 84.
- the large portion extends along the axial direction D A between an upstream end 86 and a downstream end 88.
- the small portion 82 extends radially outwards from the upstream end 86 of the large portion 84.
- the sealing tongue 8 is arranged at each junction between two ring sectors 10.
- the small portion 82 makes it possible to hold the sealing tongue 8 in position axially and to prevent it from moving downstream and that it does not damage the downstream radial flange 68 of the ring support structure 6.
- the present invention thus proposes a turbine ring assembly having a reduced number of parts, thus reducing the risk of leakage and improving the robustness of the ventilation and the sealing of the assembly while ensuring the maintenance of the ring sectors.
- made of CMC material made of CMC material.
- the turbine ring assembly according to the invention disregards the manufacturing dispersion of the CMC ring sectors and makes it possible to reduce the tangential stresses at the rings holding devices.
- the turbine ring assembly is integrable on a larger turbine range
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP22722300.5A EP4326972A1 (fr) | 2021-04-21 | 2022-04-12 | Ensemble d'anneau de turbine monté sur entretoise |
CN202280029215.9A CN117222800B (zh) | 2021-04-21 | 2022-04-12 | 安装在横向构件上的涡轮环组件 |
US18/555,801 US20240093619A1 (en) | 2021-04-21 | 2022-04-12 | Turbine ring assembly mounted on a cross-member |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2104149A FR3122210A1 (fr) | 2021-04-21 | 2021-04-21 | Ensemble d’anneau de turbine monté sur entretoise |
FRFR2104149 | 2021-04-21 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2022223905A1 true WO2022223905A1 (fr) | 2022-10-27 |
Family
ID=76601348
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2022/050688 WO2022223905A1 (fr) | 2021-04-21 | 2022-04-12 | Ensemble d'anneau de turbine monté sur entretoise |
Country Status (5)
Country | Link |
---|---|
US (1) | US20240093619A1 (fr) |
EP (1) | EP4326972A1 (fr) |
CN (1) | CN117222800B (fr) |
FR (1) | FR3122210A1 (fr) |
WO (1) | WO2022223905A1 (fr) |
Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2540939A1 (fr) | 1983-02-10 | 1984-08-17 | Snecma | Anneau d'etancheite pour un rotor de turbine d'une turbomachine et installation de turbomachine munie de tels anneaux |
EP1350927A2 (fr) | 2002-03-28 | 2003-10-08 | General Electric Company | Segment de virole, procédé de fabrication d'un segment de virole, et virole pour moteur à turbine |
US20060292001A1 (en) * | 2005-06-23 | 2006-12-28 | Siemens Westinghouse Power Corporation | Ring seal attachment system |
FR2955898A1 (fr) | 2010-02-02 | 2011-08-05 | Snecma | Etancheite amont d'un anneau en cmc dans une turbine de turbomachine |
GB2480766A (en) | 2010-05-28 | 2011-11-30 | Gen Electric | Turbine shroud |
US20120082540A1 (en) | 2010-09-30 | 2012-04-05 | General Electric Company | Low-ductility open channel turbine shroud |
US20140271145A1 (en) | 2013-03-12 | 2014-09-18 | Rolls-Royce Corporation | Turbine blade track assembly |
WO2015191186A1 (fr) * | 2014-06-12 | 2015-12-17 | General Electric Comapny | Ensemble dispositif de suspension de carénage |
WO2015191174A1 (fr) * | 2014-06-12 | 2015-12-17 | General Electric Company | Ensemble dispositif de suspension de carénage à multiples pièces |
EP3045783A1 (fr) * | 2015-01-19 | 2016-07-20 | United Technologies Corporation | Joint coulissant |
EP3118417A1 (fr) * | 2015-07-13 | 2017-01-18 | General Electric Company | Ensemble de virole pour moteur de turbine à gaz |
EP3680455A1 (fr) * | 2019-01-10 | 2020-07-15 | United Technologies Corporation | Ensembles joint d'air extérieur d'aube avec broches de support axial |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3064022B1 (fr) * | 2017-03-16 | 2019-09-13 | Safran Aircraft Engines | Ensemble d'anneau de turbine |
FR3064023B1 (fr) * | 2017-03-16 | 2019-09-13 | Safran Aircraft Engines | Ensemble d'anneau de turbine |
-
2021
- 2021-04-21 FR FR2104149A patent/FR3122210A1/fr active Pending
-
2022
- 2022-04-12 US US18/555,801 patent/US20240093619A1/en active Pending
- 2022-04-12 WO PCT/FR2022/050688 patent/WO2022223905A1/fr active Application Filing
- 2022-04-12 CN CN202280029215.9A patent/CN117222800B/zh active Active
- 2022-04-12 EP EP22722300.5A patent/EP4326972A1/fr active Pending
Patent Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2540939A1 (fr) | 1983-02-10 | 1984-08-17 | Snecma | Anneau d'etancheite pour un rotor de turbine d'une turbomachine et installation de turbomachine munie de tels anneaux |
EP1350927A2 (fr) | 2002-03-28 | 2003-10-08 | General Electric Company | Segment de virole, procédé de fabrication d'un segment de virole, et virole pour moteur à turbine |
US20060292001A1 (en) * | 2005-06-23 | 2006-12-28 | Siemens Westinghouse Power Corporation | Ring seal attachment system |
FR2955898A1 (fr) | 2010-02-02 | 2011-08-05 | Snecma | Etancheite amont d'un anneau en cmc dans une turbine de turbomachine |
GB2480766A (en) | 2010-05-28 | 2011-11-30 | Gen Electric | Turbine shroud |
US20120082540A1 (en) | 2010-09-30 | 2012-04-05 | General Electric Company | Low-ductility open channel turbine shroud |
US20140271145A1 (en) | 2013-03-12 | 2014-09-18 | Rolls-Royce Corporation | Turbine blade track assembly |
WO2015191186A1 (fr) * | 2014-06-12 | 2015-12-17 | General Electric Comapny | Ensemble dispositif de suspension de carénage |
WO2015191174A1 (fr) * | 2014-06-12 | 2015-12-17 | General Electric Company | Ensemble dispositif de suspension de carénage à multiples pièces |
EP3045783A1 (fr) * | 2015-01-19 | 2016-07-20 | United Technologies Corporation | Joint coulissant |
EP3118417A1 (fr) * | 2015-07-13 | 2017-01-18 | General Electric Company | Ensemble de virole pour moteur de turbine à gaz |
EP3680455A1 (fr) * | 2019-01-10 | 2020-07-15 | United Technologies Corporation | Ensembles joint d'air extérieur d'aube avec broches de support axial |
Also Published As
Publication number | Publication date |
---|---|
FR3122210A1 (fr) | 2022-10-28 |
EP4326972A1 (fr) | 2024-02-28 |
CN117222800B (zh) | 2024-05-10 |
CN117222800A (zh) | 2023-12-12 |
US20240093619A1 (en) | 2024-03-21 |
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